Method and apparatus for propelling projectiles for space and other applications



June 4, 1968 G. FRANCIS 3,386,380

METHOD AND APPARATUS FOR PROPELLING PROJECTILES FOR SPACE AND OTHERAPPLICATIONS Filed Jan. 4, 1967 5 Sheets-Sheet 1 INVENTOR.

GUS F RA N C I 5 A TTORNEYS June 4, 1968 G. FRANCIS 3,386,380

METHOD AND APPARATUS FOR PROPELLING PROJECTILES FOR SPACE AND OTHERAPPLICATIONS Flled Jan 4 1967 5 Sheets-Sheet 2 INVENTOR- GUS FRANCISATTORNEYS June 4, 1968 c. FRANCIS 3,386,380

METHOD AND APPARATUS FOR PROFELLING PROJECTILES FOR SPACE AND OTHERAPPLICATIONS Filed Jan. 4, 1967 5 Sheets-Sheet 3 SLIDING CAN COVER AMMOSENSING DEVICE 42 CAN z EXTENSION 0 ARMS I I D SYSTEM SLIDING CAN 2 2COVER 0 SLIDING CAN 0 9m 0 COVER 2 2 2E 2 E 5 E I n: a:

U Lu l LL! 2 Q COMPUTER I- 4 X x J m EXTENSION POWER SUPPLY ARMS AMMOSENSING DEVICE INVENTOR.

GUS FRANCIS ATTORNEYS METHGD AND APPARATUS FOR PRGPEL- LING PROJECTHLESFQR SiACE AND QTHER APPLICATEONS Gus Francis, 1480 S. Josephine, Denver,Colo. 80210 Continuation of application Ser. No. 439,866, Mar. 15, 1965.This application Jan. 4, 1967, Ser. No. 699,267 16 Claims. (Cl, 1ti2-23)ABTRAT OF THE DISCLGSURE The invention is a weapon device for hurlingwithout a projectile chamber, fiat plate projectiles against a target,and comprises an explosive charge having at least one flat face with abutter plate having opposed flat faces mounted contiguous to theexplosive charge and a flat metal projectile plate mounted contiguous tothe butler plate, the specific improvement being the use of the bufferplate to prevent premature shattering of the metal projectile plate. Amodification is the incorporation of the Weapon device using opposedmetal plates on space vehicles as it is peculiarly adaptable to use inspace where a recoilless weapon is required.

Cross reference to related applications This application is acontinuation application of my application Ser. No. 439,866 filed in theUS. Patent Ofiice on Mar. 15, 1965, and now abandoned.

This invention relates to a method and apparatus for directionallypropelling projectiles by means of explosives without the aid of aprojection chamber, and to an anti-satellite satellite weapon utilizingthe method and apparatus.

This application is related to the co-pending application of James A.Dunn and Gus Francis, Ser. No. 200,- 379, filed in the US. Patent Ofliceon June 6, 1962, now Patent No. 3,196,791, and entitled, Method andApparatus for Propelling Projectiles.

The principal use for the present invention is in antisatellitesatellite applications, that is, the use of explosive 1y propelledprojectiles launched from a satellite for the destruction of enemysatellites, or other objects in space. It is peculiarly adapted to spaceapplication wherein the absence of air, the medium for forming shockwaves by explosives, requires the use of other means than shock wavesformed by explosives for the destruction of enemy satellites.

The invention is also adapted for the use of explosively propelled metalprojectiles in self-destruct devices for rupturing fuel tanks ofmissiles and to release boosters and other mechanisms from spacevehicles and other jet propelled devices. Self destruction is requiredwhen the missile or device is off-course and has assumed an erratic anduncontrolled path of travel.

The invention will be described and illustrated in connection with bothof the above discussed applications, but it is by no means limited tothese applications.

As respects the first application, the development of anti-satellitesatellite weapons and other defensive devices for use against enemymissiles and satellites traveling in space is now a matter of primemilitary consideration. It is important to have available a means fordestruction of enemy missiles, spy satellites and other type satellitestraveling in space above the atmosphere. Conventional means for hurlingprojectiles, such as projection chambers, are out of the question foruse in space applications because of weight and space considerations forthe vehicle carrying them. Further, conventional projectile hurlnitedStates Patent D ing devices could not be used on space vehicles becausethe recoil force of these devices would knock the space vehicle carryingthem ofi course and out of its orbit. Accordingly, it is of extremeimportance to have a projectile hurling device available for use onanti-satellite satellites to defend against enemy satellites, which is lght and compact in construction and does not produce recoil forces uponprojection of the projectile toward the enemy missile or vehicle.

As respects the second application, it is now standard practice toincorporate self-destruct devices in missiles and propelling devices forspace craft to provide for automatic self-destruct of the missile orpropelling device when the missile or space-craft is off course.Ordinarily, self-destruct devices rupture fuel tanks and this results indestruction of the missile either through loss of pressure in the fueltank, loss of fuel, explosions, or for other reasons. In the case ofmissiles filled with hyper-golic propellants wherein fuel and oxidizerare carried in separate tanks, self-destruct is achieved bysimultaneously rupturing both tanks to permit the fuel and oxidizer tocome together and ignite so that the resultant violent reaction rips themissile apart, terminating the mission. Achieving self-destruct bycausing structural damage to tanks or parts of missiles is ordinarilyaccomplished with explosive bombs or shaped charges. Bombs or shapedcharges are placed against the outside fuel tank walls, against domes offuel tanks, or upon the guidance mechanism.

Conventional methods of achieving self-destruct are subject to a numberof disadvantages. The damage to missile parts must be directional andspecified and if two tanks containing hypergolic fluids are toberuptured, rupturing of both tanks must be accomplished substantiallysimultaneously. When bombs are used, the fragmentation of the metal caseis random and fragment particle sizes vary so that it is difficult toprecisely control the direction of particles with accuracy toachievedestruction in the specified areas.

When linear shaped charges are used, damage is greatest when standotfdistances are exact and predetermined and this is not always possible ofattainment. Shaped charges are more eifective in penetrating masses ofmaterial and causing damage Within a narrow specified radial diameter.When used against targets which require a wide area to be destructed,shaped charges are ineffective. Even when bombs or shaped charges can beplaced against the outside tank walls, against domes, or upon theguidance mechanisms, failures often result in propagation of the shockwave due to sharp bends or poor contact between joining strands.

A method and apparatus was disclosed in the copend ing applicationreferred to above for explosively propelling fiat plates of lead andlead alloys comparatively great distances for self-destruct spaceapplications. As further disclosed in that application, it has not beenpossible heretofore to explosively project plates of all metals andtheir alloys by the method described therein, but oniy plates of lead,and alloys thereof containing at least ten percent lead, could propelledexplosively more than a few centimeters without shattering.

It is therefore an object of this invention to provide an apparatus andmethod for propelling projectiles which can be used in outer space inconnection with an antisatellite satellite weapon.

It is another object of this invention to provide a method and apparatusfor directionally and accurately propelling projectiles either in oroutside the atmosphere without the use of a propelling chamber.

It is stiil another object of this invention to provide a method foraccomplishing self-destruct of jet propelled missiles.

It is a further object of this invention to provide a method andapparatus for simultaneously rupturing a plurality of missile fuel tanksfor the propose of selfdestructing the missile.

It is another object of this invention to provide a method and apparatusfor accomplishing self-destruct of missiles in outer space where thecreation of shock waves is impossible because of the absence of air.

It is another object of this invention to provide a means for propellingthin plates of metal in general over great distances without shattering.

The invention includes a method for directionally propelling projectileswhich consists, in one modification, in fitting one surface of asubstantially fiat metal plate which serves as the projectile over acorresponding surface of a sheet of explosive with a sheet of protectivematerial such as plastic, serving as a buffer plate, between the metalplate and the explosive, and detonating the explosive to propel themetal plate flat-wise along a desired path with controlled accuracy.This modification provides for the destruction of one object only. Theapparatus formed of explosive and metal plates is referred to herein asa destruct charge.

If the simultaneous destruction of two objects or two or more walls,such as, the walls of two propellant tanks of a missile is required, ametal plate with the buffer plate between it and the explosive charge isarranged on each side of the explosive charge to form a modifieddestruct charge and the assembly positioned between the two walls sothat upon detonation of the explosive the walls will be substantiallysimultaneously ruptured by the plates.

In space applications, wherein the device is used in anti-satellitesatellite applications the destruct charge or projectile assembly ismounted on a satellite and fired at another object traveling in space,with the use of fire control apparatus, the latter in combination withthe projectile assembly constituting one modification of the invention.In the space application, it is generally expedient to use two plates inthe projectile assembly even though the destruction of only one targetis intended. This is because the use of a back-up plate provides a basefor the plate which is being directed at the target to aid in keeping iton its flight path, and it also serves a recoil counteracting function.It is also deisrable to use two destruct charges located on oppositesides of the vehicle to control or cancel out recoil forces.

The invention is best explained by reference to the accompanyingdrawings in which like parts are represented by like numerals, and inwhich,

FIG. 1 is a top plan view of the destruct device used in ananti-satellite satellite or as a self-destruct device;

FIG. 2 is a cross sectional view of the destruct device taken on line2-2 of FIG. 1;

FIG. 3 is a cross sectional view of a modification of the destructdevice of FIG. 2 in which single plates of lead and plastic are used;

FIG. 4 is a schematic showing of the destruct device arranged betweenpropellant tanks, one containing oxidizer and the other containing fuel,the mixture of fuel and oxidizer forming a hypergolie mixture;

FIG. 5 is a schematic perspective view of a modification of the destructdevice in which a rectangular shaped wafer is used, the case beingomitted in this showing,

FIG. 6 is a schematic showing of a weapon satellite carrying theprojectile assembly or destruct device of this invention andillustrating its application in space as an anti-satellite satellite,and

FIG. 7 is a schematic sectional showing of the weapon satellite of FIG.6 showing schematically the various operating components of thesatellite.

Referring to FIGS. 1 and 2, the weapon or destruct device representedgenerally by the numeral 10 comprises a solid explosive charge 12 havingfiat, parallel outer longitudinal faces 14 and 16 which are abutted bycorrespondingly flat buffer plates or wafers 18 and 20 of protectivematerial. These plates are made with parallel longitudinal fiat faceswhich correspond with the flat faces 14 and 16 of the explosive charge12. Flat metal plates 22 and 24 are held securely against the protectiveplates 18 and 29, respectively, by a metal case comprising a back plate26 and a circular facing cover or cap 28, which is cup-shaped andprovided with a circular horizontal flange 30 which is attached to backplate 26 by means of rivets 32 or other equivalent fastening means. Itwill be noted that the back plate 25 and cover 28 conform to thesurfaces of the metal plates 20 and 22 and hold the entire assemblytogether in snug relationship. A dctonator 34 is mounted at one end ofthe cover 28 in contact with the explosive charge 12. The purpose of thedetonator is, of course, to initiate the shock wave which builds up todetonate the explosive 12 to propel metal plates 22 and 24 outwardly inopposite directions. The back plate 26 and facing cover 28 are made ofreadily llangihle material such as aluminum or similar supportingmaterial.

It is an important feature of the invention that the metal plates andbuffer plates correspond and mate with the longitudinal fiat faces ofthe explosives. It is this feature which provides directionality to thepath of the metal plates and permits accurate propelling of these platesalong a required trajectory. In the modifications shown, the faces ofthe explosive charge are parallel; however, the invention is notnecessarily restricted to this requirement as obviously the flat platescould be propelled angularly to each other with the use of non-parallelfaces on the explosive charge. It has been found that they can bepropelled in. a straight line perpendicular to the explosive face if thefaces of the explosive are fiat and the mating faces of protective plateand explosive correspond with each other.

Any conventional explosive may be used, such as, TNT, PBX, CompositionA, PETN or other type high explosives. The material of the protective orbutter plates 18 and 29 may be chosen from a large number ofnon-metallic materials, preferably nylon, Teflon and fiber glass in aplastic matrix, or various plastics. The manner in which this materialoperates to prevent the metal plates 22 and 24 from shattering under theloading of the shock Wave from the detonation of the explosive charge 12is not known. These plates are referred to herein as protective platesor buffer plates to describe generally their function. Obviously, manynon-metallic materials will function in this application and theinvention is not restricted to the use of the recited materials as thereare many equivalent plastics and other materials which will operate justas effectively. The detonator 34 may be made of conventional design andits construction is not critical.

The metal or alloy from which the metal plates 22 and 24 are constructedis not critical as all metals are suitable when used with the protectiveplates. Illustrative operative metals are silver, gold, cadmium, cobalt,chromium, copper, molybdenum, nickel, lead, tin, thorium, titanium,tantalum, vanadium, tungsten, zirconium, bismuth, iron, antimony, andalloys of these metals. Prior to this invention, as disclosed in theabove-referred to application, the only metals known to be operative inthe atmosphere without the protective plates were lead and alloys oflead containing at least ten percent lead as other metals shatter in theatmosphere under explosive loading after a few inches of travel.However, it has been found that with the use of the protective plates 18and 20, all other metals can be used. Mercury can be used by incasing itin a suitable casing which conforms with the fiat surfaces of theprotective plates. The detonator 34 may be of conventional design andits construction is not critical.

Reference is now made to FIG. 3 in which there is shown a modificationutilizing a single metal plate 22, a single protective plate 20 andexplosive 12, the assembly of explosive, protective plate and metalplate being surrounded by a protective casing comprised of back plate 26and cover 28. The detonator 34 in this instance is positioned centrallyof the explosive charge on the side opposite the prospective target asshown.

In FIG. 4 the application of the destruct device as a self-destructdevice is illustrated. It is positioned between two propellant tankdomes 38 and 40 of a missile or space vehicle and in this applicationthe tanks are ruptured substantially simultaneously by the metal plateson either side of the explosive when the explosive is detonated.

In FIG. 5, there is shown a modification of the weapon device comprisedof a flat metal rod and a flat rod of explosive having a protective rodof plastic .or like material between them, the length dimension of thecomponents being large in relation to the width dimension.

It is essential that the projectile plates of the destruct device beprojected directionally and with accuracy. This is accomplished bymaking the mating surfaces of explosive, buffer plate and metal fiatwith no substantial voids in them. The amount of explosive used will ofcourse be a factor in the velocity with which the plates are propelled.The size of the metal plates will also, obviously be a factorcontributing to the velocity of the plates and the distance they will bepropelled.

The destruct device of the invention was extensively tested using platesof various dimensions of a large number of metals, including thosetested in the examples given below, without the protective plate ofplastic positioned between explosive and metal. With the exception oflead and lead alloy plates all others shattered in no more than four orfive centimeters of travel. The device was extensively tested with anumber of metals using a protective plate of plastic between the metaland explosive and the following examples were selected from the tests.In these examples the double metal plate modification of FIG. 2 wasused. In order to provide comparative results, an arrangement of a leadplate without the protective plate was used on one side of the explosiveas a blank and a metal plate, hereinafter referred to in the examples asthe plate being tested," with a protective plate of nylon between it andthe explosive was used on the opposite side of the explosive. Lead wasused for the blank because it is the only metal from which a plate canbe constructed which will not shatter if explosively propelled even afew centimeters without a protective plate positioned between it and theexplosive before detonation. The metal plates used were 7 inches indiameter and inch thick. The protective plate was made of nylon 7 inchesin diameter and /8 inch thick. In all of the examples, the charge wassupported by a wooden frame and was placed between two 55 gallon steelbarrels a distance of 16 feet from each barrel with the flat sides ofthe unit facing the target barrels, with the exception that in Examples3 and 4 the destruct device was 12 feet from the barrels.

Example 1 In the destruct device used in this example the metal platebeing tested was constructed of lead. At the firing, the results of thistest showed that the lead plate being tested produced a larger hole inits target barrel than did the lead plate being used as the blank. Thesize of the hole produced by the lead plate being tested was 6 inches by8 inches.

Example 2 The destruct device used in this example had a steel plate asthe plate being tested. Upon firing the device, the steel plate produceda hole in its target 12 inches by 8 inches, while the lead plate used asa blank produced a hole 4 inches by 6 inches.

Example 3 In this example the plate being tested was a brass plate. Uponfiring, the brass plate completely destroyed the barrel with the sidesof the barrel being peeled back almost in a straight line. The leadplate split the side of the barrel the entire length and peeled thesides back approximately only half way around.

Example 4 In this example the destruct charge used had an aluminum plateas the plate being tested. Upon firing, the aluminum plate produced ahole in the target about 4 inches by 8 inches while the lead plateproduced a hole 18 inches by 24 inches. It would appear that the leadplate was more effective in this example; however, there was noobjectionable shattering of the aluminum plate and it produced a hole ofsubstantial size for a relatively frangible metal of this type.

Example 5 In this test another steel plate was used as the metal beingtested. The steel plate formed a hole 12 inches by 18 inches in thetarget.

The examples graphically demonstrate that by the use of the protectivebutler plate between the explosive and the metal plate, plates of metalsother than lead can be explosively propelled at least 12-16 feet in theatmosphere without shattering and they are as efifective for destructionof the target as lead plates used Without buffer plates. Example 1 showsthat the use of a protective plate between 2. lead plate and theexplosive adds to the effectiveness of the lead plate in the destructionof targets. In con trast to these results, many tests in which attemptswere made to explosively propel plates made of metals other than leadwithout bulfer plates showed that such plates of the size used in theexamples could not be propelled more than a few inches withoutcompletely shattering and breaking apart.

It is seen from the above description that a method has been providedfor directionally launching metal projectiles in the form of plateswithout the use of a projectile barrel. The method provides for theutilization in this manner of all types of metals. Plates made of anymetal can be explosively propelled great distances Without shattering.This invention makes possible the use of the destruct device inanti-missile-missiles and anti-satellite satellite devices.

Reference is now made to FIGS. 6 and 7 for a showing of the applicationof the destruct device in an anti-satellite satellite weapon system, theshowing broadly depicting the combination of the destruct device with afire control system transported on a satellite. The satellite carryingthe destruct device is designated by the numeral 42. The systems carriedby the satellite for launching the destruct charges comprise means forstoring the destruct charges such as destruct charge magazines or ammocans, means for computing the range and velocity of the target such as alocator and range-velocity computer, means for stabilizing thesatellite, means for directing the operations of the satellite, such"as, a control telemetry transmitter, means for identifying the targetsuch as a conventional IFF system and means for supplying power tooperate the various systems. The systems outlined above for transportingand launching the destruct charge may be conventional systems commonlyused to perform the functions indidated. They are illustrative ofoperative systems in use which can be used on the anti-satellitesatellite weapon to provide an operative modification.

Referring to FIG. 6, six destruct charge projectile holders 44 are shownequally spaced around the satellite. The number used is not limited tosix as any convenient number may be used. Each projectile holder issupported by the telescoping arm 46. In the preferred modification, thetelescoping arms are stored inside the satellite as shown schematicallyin FIG. 7 and may be propelled into position with the destruct chargemounted thereon by means of a pyrotechnic propellant or other equivalentmeans which is automatically actuated upon the firing of one of thecharges or which may be actuated by remote control. The telescoping armsare so mounted that when one is propelled into position it automaticallyejects the arm it replaces and from which the charge has just beenfired. The satellite can, of course, be operated without replenishmentprojectiles. The magazine for the destruct charges and telescoping armsat each station can be constructed to hold as many charges as necessary.If desired, the final charges may be so designed as to destruct thesatellite itself so as to remove it from orbit or demolish it so that itwill be unidentifiable by enemy inspection.

The target locater land range-velocity computer may be either groundcontrolled or self-directed upon operating instructions from earth.Approximate target vectors can be furnished the computer by earthtelemetry and a conventional satellite target finding system located onthe satellite takes over and uses this information for the finallocation of the target for its destruction. The target location systemto be used may be a miniaturized Doppler radar system and/or a systemsimilar to conventional radar directed anti-aircraft systems.

The destruct charges 10 are mounted in the projectile holders to rotateabout the axis upon which they are mounted by conventional, directionaldrive mechanism. The telescoping arms 46 are also mounted to rotatearound their long axes with the result that the destruct charges 10 canbe rotated about two perpendicular axes in aiming them at a target.Conventional actuating means responsive to a control telemetrytransmitter are provided for rotating the telescoping arms and destructcharges in response to information provided by the target locater andrangevelocity computer.

Telescoping antenn'as 43 are shown spaced around the satellite forreceiving signals for the various systems.

The firing system is constructed for coordination to provide formovement of the bidirectional charge to a predetermined firing positionby Selsyn motors and to provide for stabilization of the charge prior tofiring. This is facilitated by the fact that no media exists in outerspace to change a targets course and speed.

A control telemetry and transmitter system is built in to direct theoperations of the satellite. It functions to turn on the power supply,turn on the transmitters, supply the arming signal for the charges, plotin the targets approximate course and direction and, after firing, todeactivate the components of the apparatus.

In the preferred modification, a conventional IFF system is installed toprevent accidental destruction of friendly satellites and to insuredestruction of enemy satellites. It is anticipated that attempts may bemade to board the satellites by enemy inspection parties. An IFF systemis necessary to ascertain whether the boarder or target satellite isfriend or enemy. Failure of proper identification of the other satelliteresults in immediate automatic actuation of the major power supply andarming systems and destruction of the boarders by the bidirectionalcharges.

Power for the satellite is furnished by solar energy collected withmirrors represented schematically at 50 in accordance with conventionalprocedures. The power supply system is conventional and uses standardbattery rechargeable cells utilizing solar energy to operate the siliconsolar power generating sources. These power generating sources are builton the missile or they can be on a trailing tail-type of appendage. Thepower required to operate the satellite will be large when all systemsare on a go basis but minimal when they are on a stand-by basis.

From the above description it is seen that the invention provides aneffective anti-satellite satellite weapon for use in space against enemysatellites in which an effective destructive charge is provided whichdoes not require the use of a projectile barrel and can be utilized on asatellite without excessive weight requirements. In this application ofthe weapon device in space, the fiat plates will travel great distancesin a straight line as there is no effect on them from gravity or anatmosphere. The advantage of this application is readily seen because itdoes not require heavy launching equipment to be carried by thesatellite where space and weight requirements are at a premium. Use ofconventional weapons are prohibitive because of the large weight andspace occupied by these weapons. Furthermore, these conventional weaponsproduce a recoil effect which would make it impossible to keep thesatellite on its course.

The invention has been described by its application as a self-destructdevice for simultaneously destructing opposing walls of missile fueltanks and in an anti-missilemissile. Obviously, it is by no meanslimited to these applications as they are given for the purposes ofillustration only. The invention may be used in a single projectiledevice shown in FIG. 3 for various purposes as well as in the dualprojectile device of FIG. 2. The device finds use in any applicationwherein it is necessary or advantageous to propel a projectile withoutthe use of a projectile chamber. The invention has many applications foruse in connection with space vehicle and missiles traveling in theatmosphere, or in outer space wherein conventional explosives cannot beused to effect damage by traveling shock waves.

While the term plate has been used herein to describe the metalprojectile, this is not to be considered as restricting the shape of theprojectile as practically any shape of projectile can be used, the mainrequirement being that the adjacent surfaces of explosive and protectiveplate and of protective plate and explosive conform and be substantiallyflat.

It is therefore to be understood that various modifications and changesmay be made in the construction and arrangement of parts of the presentinvention without departing from the spirit and scope thereof as definedby the appended claims. Various changes and modifications may be made incarrying out the present invention without departing from the spirit andscope thereof. Insofar as these changes and modifications are within thepurview of the annexed claims, they are to be considered a part of thisinvention.

What is claimed is:

1. The method of substantially simultaneously rupturing a plurality ofspaced apart walls by hurling projectiles against them without the useof a projectile chamber which comprises: positioning a piece ofexplosive material having at least two fiat opposed faces between saidspaced apart walls with each fiat face of explosive facing a Wall;supporting a fiat buffer plate having opposed first and second flatsurfaces contiguous to each of said opposed faces of explosive withcontiguous faces of explosive and first surfaces of buffer platesconforming to each other; supporting a metal plate having at least oneflat face contiguous to each of said second fiat surfaces of the bufferplates with the flat faces of the metal plates conforming with thecontiguous second surfaces of the buffer plates; and detonating saidexplosive charge to simultaneously and directionally propel said platesflatwise against said walls to rupture them with a greater destructiveeffect than would be achieved without the use of said buffer plates.

2. The method of claim 1 in which said spaced apart walls are walls offiuid tanks containing fluids to be mixed and the shattering of saidwalls results in mixing of said fluids.

3. The method of rupturing a Wall of a body by hurling a projectileagainst it without the use of a projectile chamber which comprisessupporting a fiat metal plate having frontal surface dimensions greaterthan its thickness in front of said wall with one face of the metalplate facing a wall and in line therewith and the other face of saidplate contiguous to and conforming to a fiat face of a flat buffer platewhich is supported with its other flat face contiguous to acorresponding fiat face of an explosive charge; and detonating saidexplosive charge to propel said metal plate directionally against saidwall to rupture assasao f3 it with a greater destructive effect thanwould be achieved without the use of the buffer plate.

4. The method of destroying objects traveling in space by hurlingprojectiles against them without the use of a projectile chamber whichcomprises mounting on a space vehicle a destruct charge comprising anexplosive charge having opposing fiat faces with a fiat buffer platehaving opposed fiat surfaces and a flat metal plate having at least onefiat face supported adjacent each fiat face of the explosive charge inthe order recited and the contiguous fiat faces of metal plates andbuffer plates and buffer plates and explosive charge conforming to eachother; positioning said destruct charge so that the exposed face of oneof the metal plates is aimed along a collision course with said object;and detonating said explosive charge; whereby said metal plates arepropelled in opposite directions with said one of the metal platespropelled along said collision course into said object to strike it witha greater destructive force than would be achieved without the use ofsaid buffer plates.

5. A device for propelling a projectile towards a target without the useof a projectile chamber comprising: a barrelless support member; a highexplosive charge having at least one flat face and mounted on saidbarrelless support member; a buffer plate having a first flat facecoutiguous and precisely conforming to a fiat face of said explosivecharge, and a second flat face; a metallic plate having at least oneflat face; said buffer plate located between said explosive charge andsaid metallic plate with its second fiat face contiguous to andprecisely conforming to a flat face of said metallic plate; anddetonating means connected to said high explosive for detonating saidcharge; whereby upon detonation of said detonating means said metallicplate is directionally propelled towards said target without the use ofa projectile chamber to provide a greater destructive effect uponstriking said target than would be achieved without the use of saidbuffer plate.

6. The desctruct charge of claim 5 in which the buffer plate is made ofnon-metallic material.

7. The destruct charge of claim 5 in which the buffer plate is made ofplastic material.

8. The destruct charge of claim 7 in which the buffer plate is made of amaterial from the class consisting of nylon andpolytrifiuorochloroethylene.

9. The destruct charge of claim 8 in which said buffer plates are madeof non-metallic material.

10. The destruct charge of claim 8 in which said buffer plates are madeof a plastic.

11. The destruct charge of claim 8 in which the buffer plates are madeof a material from the class consisting of nylon andpolytrifluorochloroethylene.

12. A device for propelling a projectile towards a target without theuse of a projectile chamber comprising: a barrelless support member; ahigh explosive charge having opposed flat faces mounted on saidbarrelless support member; a buffer plate having opposed fiat surfacessupported on each side of said explosive charge with a flat face of theexplosive charge and one fiat face of the bufier plate contiguous andconforming to each other; a metal plate having at least one flat facesupported contiguous to each of said buffer plates with a frat face of ametal plate and the other flat surface of a buffer plate contiguous andconforming to each other; and detonating means connected to said highexplosive for detonating said charge; whereby upon detonating saiddetonation means said metallic plate is directionally propelled towardssaid target without the use of a projectile chamber to provide a greaterdestructive effect upon striking said target than would be achievedwithout the use of said buffer plate.

13. A weapon system for destroying an object travelling in space withoutthe use of a projectile chamber comprising: in combination, a spacevehicle; a destruct charge supported on said space vehicle comprising anexplosive charge having opposed flat surfaces; a flat metal plate havingopposed flat faces supported adjacent each of the fiat surfaces of saidexplosive charge; a fiat buffer plate having opposed flat facessupported between said explosive charge and each of said metal plateswith its fiat faces contiguous to and conforming to the respective flatfaces of explosive and metal plates; means for positioning said destructcharge so that the exposed face of one of the metal plates is aimedfiat-wise on a collision course with said object; and means fordetonating said explosive to propel said metal plates in oppositedirections and said one metal plate directionally along said collisioncourse to provide a greater destructive effect upon striking said objectthan would be achieved without the use of said buffer plate.

1d. The Weapon system of claim 13 in which the buffer plates are made ofnon-metallic material.

15. The weapon system of claim 13 in which the buffer plates are made ofplastic.

16. The weapon system of claim 13 in which the buffer plates are made ofa material from the class consisting of nylon andpolytrifiuorochloroethylene.

References Cited UNITED STATES PATENTS 2,573,362 10/1951 Rouse 102--382,911,911 11/1959 White 102-38 2,933,980 4/1960 Moore et al 244-319 X3,054,329 9/1962 Willig .a 898 X 3,196,791 7/1965 Francis et al. 10223OTHER REFERENCES Aviation Week, Space Technology, Oct. 3, 1960, pp.54-63.

BENJAMIN A. BORCHELT, Primary Examiner.

V. R. PENDEGRASS, Assistant Examiner.

